Abstract: The present paper briefly reviews the domestic research work,during past ten years, on subsonic and transonic S-shaped inlet used in missiles and summarizes some progress in recent years in inlet design,numerical methods for the calculation of flow fields inside and outside inlet, inlet/engine compatibility, measuring and testing technology, and data processing etc. Up to now, the basic design criterions, the methods to determine the inlet/engine compatibility conditions in test and the simulation of coming air flow conditions have been proposed,and numerical methods have been used in choice of the shapes of the lips and the turning passage,and the methods for measuring the outlet pressure pattern under stable conditions and the corresponding data processing have also been studied. The total pressure recovery σ=0.98-0.99,total pressure distortion DC60 = -0.20--0.30 and total pressure nonuniformity D= 5% are obtained at highsubsonic speed with fineness ratios of 3.5-5 and axis defection angles of 35°-38.5°.

Key words: Subsonic inlet;Transonic inlet

摘要： 本文简要回顾了十年来国内弹用亚、跨音速S形进气道的研究工作,从进气道设计,进气道内外流场数值计算,进气道/发动机匹配,测试技术和数据处理等方面,扼要叙述了近年来所取得的一些进展.

关键词: 亚音速进气道;跨音速进气道